Target interception

ABSTRACT

A projectile deployment system for use in a intercepting target ( 32 ) wherein the system includes a body ( 10 ) defining a body axis, and a number of barrels ( 30 ) circumferentially spaced around the body axis. Each of the barrels ( 30 ) contains a number of projectiles ( 31 ) axially stacked therein, with a corresponding number of charges being provided such that each charge is associated with a respective projectile ( 31 ) along barrel ( 30 ). Each of the charges is individually activated to deploy a respective projectile ( 31 ) in response to a signal from a controller.

BACKGROUND OF THE INVENTION

The present invention relates to a projectile deployment device for usein a target intercept device, and method for intercepting a target andin particular to projectiles deployment devices for use in kill vehiclesand missile defence systems for intercepting missiles such as ballisticmissiles.

DESCRIPTION OF THE PRIOR ART

The reference to any prior art in this specification is not, and shouldnot be taken as, an acknowledgment or any form of suggestion that theprior art forms part of the common general knowledge.

There are a number of fundamental difficulties involved in theinterception of an incoming enemy ballistic missile with a conventionalinterception missile or other similar kill vehicle. In particular,engineering a hit-to-kill interception missile that can achieveintercept with any consistency is problematic, principally because ofthe high converging speed of the target ballistic missile and theinterception missile.

Thus the speed of both the incoming missile and the interception missilemake tracking the incoming missile to within a hit-to-kill margin oferror, extremely difficult. Present missile tracking technologies arequite sophisticated, however the problem remains that often quitesignificant changes in the trajectory of the interception missile arerequired but are difficult to execute.

This problem is exacerbated by the fact that typical conventionalinterception missiles have a relatively small cross-sectional diameterwhich must intercept either the front or side of the incoming enemymissile, which also has a very small cross-sectional area. Thus, thisprovides a small collision cross section, meaning it is difficult toachieve the required degree of control to enable the interceptionmissile to be in exactly the right place at the right time to achieve adirect hit and thereby eliminate the target missile.

Accordingly, whilst a guaranteed hit is the ultimate goal, it isadvantageous if an interception missile could be permitted to miss itstarget and yet still have an excellent chance of disabling the missile,through the use of secondary projectile impacts.

One known solution to this is to provide the interception missile with afragmentation warhead, which is detonated before the projected impact.In this case, the fragmentation causes shrapnel to be spread away fromthe interception missile, thereby increasing the chance of a hit on theenemy missile. However, the majority of current fragmentation techniquesutilise the detonation of an explosive charge, to project shrapnel awayfrom the missile and do not provide a homogenous fragmentation pattern,but rather result in random and extremely haphazard shrapnel dispersion.

The fragmentation pattern of a simple detonation is depicted in FIG. 1,which shows a detonation occurring at 1, and which results in anexpanding sphere 2 of shrapnel fragments 3. As shown in the expandedportion the shrapnel fragments 3 are distributed randomly and do notensure a hit on an enemy missile 4, which can pass through the outwardlyexpanding radius of the sphere 2. This means that the fragmentationradius of a detonation cannot be relied upon to increase the allowablemargin of error in interception time and position of the interceptionmissile or kill vehicle. In this regard it should be noted that thediagrams presented in this specification are necessarily not to scale,and are provided merely by way of representation.

An additional problem with missile interception is that divertpropulsion technologies are limited in their effect due to the size andweight of the interception missile, as well as its speed. The angle ofinterception of the missile can be changed by ejecting mass from themissile at an angle to the direction of travel. The capability ofcurrent divert propulsion systems is severely limited by the very smallmass ejected in order to affect changes in trajectory.

Modern ballistic missiles, such as long range ICBMs (intercontinentalballistic missiles), can be designed to deploy multiple decoys and livewarheads during flight. Accordingly, an interception missile fordefeating this threat must employ a large range of sensory technology inorder to select or discriminate the live warheads from the decoywarheads.

There is not believed to be any technology currently available tosatisfactorily address this threat.

Accordingly, it will be appreciated that the ability of missiles tointercept targets including other target missiles is currently limited.

SUMMARY OF THE PRESENT INVENTION

In a first broad form the present invention provides a projectiledeployment system for use in a target intercepting device, theprojectile deployment system including:

-   -   a) A body defining a body axis;    -   b) A number of barrels circumferentially spaced around the body        axis,    -   c) A number of projectiles axially stacked along each barrel;    -   d) A number of charges, each charge being associated with a        respective projectile to urge the respective projectile along        the barrel upon activation to thereby deploy the projectile.

Typically:

-   -   a) The body includes a support body defining the number of        barrels, the barrels being adapted to receive the projectiles        and associated charges at predetermined positions; and,    -   b) The body including a number of connectors extending        therethrough for connecting first and second connections        provided on each projectile to a controller.

The controller is preferably housed in a cavity in the support body.

The first and second connections of each projectile can be coupled to anignition means for activating the charge associated with the respectiveprojectile.

The connectors typically include:

-   -   a) A number of sets of first connectors, each set of first        connectors coupling the first connections of each of the        projectiles in a respective set of barrels to the controller;        and,    -   b) A number of second connectors, each second connector coupling        the second connections of selected projectiles in different sets        of barrels to the controller, thereby allowing the controller to        apply activation signals to selected ones of the sets of first        connectors and the second connectors to thereby deploy selected        projectiles.

The body can alternatively include a support member having a number ofbarrels mounted thereon.

In this case, typically:

-   -   a) Each projectile is associated with ignition means for        activating the charge associated with the respective projectile;    -   b) Each barrel is provided with respective barrel connectors for        connecting to the ignition means, the connectors extending along        the barrel to a breach end; and,    -   c) A number of connectors provided in the support member, the        connectors being adapted to cooperate with the barrel connectors        to thereby couple the ignition means to a controller.

The support member typically includes a cavity for receiving thecontroller.

The projectile deployment system can include a controller for deployingthe projectiles by:

-   -   a) Activating the charge associated with the projectile        positioned nearest to a muzzle end of one or more selected        barrels;    -   b) Repeating step (a) to thereby fire the projectiles        sequentially from the barrel.

The controller is preferably adapted to selectively activate the chargesto thereby deploy the projectiles in accordance with a projectiledeployment pattern.

The controller typically activates the charges by applying apredetermined activation pulse thereto. Typically the projectiledeployment system includes one or more firing circuits for generatingthe activation pulses.

The controller can be adapted to fire the charges at predetermined timeintervals to thereby control the rate of deployment of the projectiles.

The controller can include:

-   -   a) A store for storing pattern data representing one or more        predetermined projectile deployment patterns; and,    -   b) A processor adapted to:        -   i) Determine the position of the target with respect to the            projectile deployment system;        -   ii) Select a projectile deployment pattern in accordance            with position of the target; and,        -   iii) Selectively activate the charges in accordance with the            pattern data.

The projectile deployment system may include one or more sensors forsensing the target, the processor being adapted to monitor the sensorsto thereby determine the position of the target with respect to theprojectile deployment system.

The controller can be coupled to a remote sensing system via acommunications system, the remote sensing system being adapted to:

-   -   a) Determine the position of the target with respect to the        projectile deployment system; and,    -   b) Transfer an indication of the target position to the        controller via the communications system.

The pattern data may indicate at least one of:

-   -   a) The barrels from which projectiles should be fired; and,    -   b) The rate of deployment of the projectiles.

At least some of the barrels generally extend radially outwardly fromthe body axis.

The projectile deployment system can include at least one planar barrelarray, the planar barrel array including a number of barrels extendingradially outwardly from the body axis so as to define a planeperpendicular to the body axis.

The projectile deployment system typically includes a number of planarbarrel arrays spaced apart along the body axis.

At least some of the planar barrel arrays can be skewed with respect toeach other such that at least one of the planar barrel arrays deploysprojectiles in a direction different to at least one other planar barrelarray.

The barrels of adjacent barrel arrays may be partially interleaved.

One or more of the planar barrel arrays may be rotatably mounted to thebody to thereby rotate about the body axis.

At least some of the barrels may extend in a direction parallel to thebody axis.

At least some of the barrels may define a barrel array for deployingprojectiles in directions along and outwardly from the body axis.

The projectile target intercepting device can be a kill vehicle, thekill vehicle including;

-   -   a) A propellant system for propelling the kill vehicle; and,    -   b) A flight controller, the flight controller being adapted to        control the propellant system to thereby control the kill        vehicle trajectory.

The propellant system can be adapted to be propelled in a directionsubstantially parallel to the body axis. The projectile targetintercepting device may alternatively be a missile.

In a second broad form the present invention provides a method ofmanufacturing a projectile deployment system, the method including:

-   -   a) Providing a body member defining a body axis;    -   b) Providing a support material surrounding the body member, the        support material including a number of first and second        connectors embedded therein;    -   c) Drilling a number of holes in the support material to thereby        define one or more barrels, the barrels being circumferentially        spaced around the body axis and being adapted to intersect        selected ones of the first and second sets of connectors; and,    -   d) Inserting projectiles and associated charges into the        barrels, the projectiles including first and second connections,        the projectiles being aligned such that:        -   i) The first connections of each of the projectiles in a            respective set of barrels are coupled to a respective set of            first connectors; and,        -   ii) The second connections of respective projectiles in            different sets of barrels are coupled to respective second            connections.

The method can include:

-   -   a) Mounting a control system within a cavity in the body member;        and,    -   b) Coupling the control system to the sets of first connectors        and the second connectors.

The method typically includes manufacturing a projectile deploymentsystem according to the first broad form of the invention.

In a third broad form the present invention provides a method ofmanufacturing a projectile deployment system, the method including:

-   -   a) Providing a body member defining a body axis;    -   b) Coupling a number of barrels to the body member, the barrels        being circumferentially spaced around the support axis, the        barrels including a number of connectors;    -   c) Inserting projectiles and associated charges into the        barrels, the projectiles including first and second connections        adapted to be aligned with respective ones of the number of        connectors; and,    -   d) Mounting a control system in the cavity, the control system        being coupled to the connectors to allow the projectiles to be        deployed.

The method typically includes manufacturing a projectile deploymentsystem according to the first broad form of the invention.

In a fourth broad form the present invention provides apparatus forintercepting a target, the apparatus including:

-   -   a) A projectile deployment system having:        -   i) A body; and,        -   ii) A number of projectile systems mounted to the body, each            projectile system being adapted to deploy a number of            projectiles in a predetermined direction with respect to the            body; and,    -   b) A controller, the controller being adapted to selectively        activate one or more of the projectile systems to thereby deploy        projectiles in accordance with a projectile deployment pattern.

The apparatus may include:

-   -   a) A vehicle having a vehicle body defining a vehicle axis;    -   b) A propellant system for propelling the vehicle; and,    -   c) A flight controller, the flight controller being adapted to        control the propellant system to thereby control the vehicle        trajectory.

The apparatus can include a projectile deployment system according tothe first broad form of the invention.

The projectile deployment system can be aligned such that the vehicleaxis is substantially coaxial with the body axis.

The deployment of each projectile can cause a reactive force along therespective barrel, the pattern of projectiles being at least one of:

-   -   a) Symmetric around the body axis to thereby equalise the        reactive forces on the body; and,    -   b) Non-symmetric around the body axis to thereby generate        non-symmetric reactive forces, thereby causing deflection of the        body.

The firing pattern of the projectiles may be adapted to control thetrajectory of the vehicle.

The target can be a missile.

The projectile deployment pattern can be selected to thereby increasethe effective cross sectional area of the vehicle.

The controller typically includes:

-   -   a) One or more sensors for sensing the target; and,    -   b) A processor adapted to:        -   i) Monitor the sensors to thereby determine the position of            the target with respect to the missile;        -   ii) Determine a projectile deployment pattern;        -   iii) Select one or more of the projectile systems in            accordance with the projectile deployment pattern; and,        -   iv) Activate the selected projectile systems.

The controller can include a store for storing pattern data representinga number of different projectile deployment patterns, the processorbeing adapted to select one of the stored projectile deployment patternsin accordance with the position of the target.

The vehicle is typically at least one of a kill vehicle and a missile.

In a fifth broad form the present invention provides a missile forintercepting a target, the missile including:

-   -   a) A missile body defining a missile axis; and,    -   b) Apparatus according to the fourth broad form of the        invention.

In a sixth broad form the present invention provides a method ofintercepting targets, the method including:

-   -   a) Launching a device at the target, the device including:        -   i) A body; and,        -   ii) A number of projectile systems mounted to the body, each            projectile system being adapted to deploy a number of            projectiles in a predetermined direction with respect to the            body; and,    -   b) Selectively activating one or more of the projectile systems        to thereby deploy projectiles in accordance with a projectile        deployment pattern such that at least one of the projectiles        intercepts the target.

The method may include:

-   -   a) Determining the position of the target with respect to the        device;    -   b) Select a projectile deployment pattern in accordance with        position of the target; and,    -   c) Activating the projectile systems in accordance with the        selected projectile deployment pattern.

Each projectile system typically includes:

-   -   a) A barrel defining a barrel axis extending from a breach end        to a muzzle end;    -   b) A number of projectiles axially stacked along the barrel        axis; and,    -   c) A number of charges, each charge being associated with a        respective projectile, and being adapted to urge the respective        projectile along the barrel to thereby deploy the projectile,        the method including selectively activating the charges to        thereby generate the selected projectile deployment pattern.

The method is preferably performed using at least one of:

-   -   a) A projectile deployment system according to the first broad        form of the invention; and,    -   b) Apparatus according to the fourth broad form of the        invention.

BRIEF DESCRIPTION OF THE DRAWINGS

An example of the present invention will now be described with referenceto the accompanying drawings, in which:—

FIG. 1 is a schematic diagram of a fragmentation pattern generated by aprior art missile;

FIG. 2 is a schematic diagram of a missile incorporating a number ofbarrel assemblies;

FIG. 3 is a schematic cross section of one of the barrel assemblies ofFIG. 2;

FIG. 4 is a schematic representation of a sequence of projectiles firedfrom the barrel assembly of FIG. 3;

FIG. 5 is a schematic diagram of a first example of a barrel array;

FIGS. 6A and 6B are schematic diagrams showing the position of a line ofdeployed projectiles relative to a target missile;

FIG. 6C is a schematic diagram showing the use of projectile deploymentin cancelling recoil forces;

FIG. 6D is a schematic diagram showing the relative positions of atarget missile and projectile line;

FIG. 7 is a schematic diagram showing the deployment of projectiles in agrid;

FIGS. 8A and 8B are schematic diagrams showing the size of a targetmissile and the relative separation of projectiles in the griddeployment pattern;

FIGS. 9A to 9C are schematic diagrams of an arrangement of a number ofbarrel arrays to form a matrix;

FIG. 10 is a schematic diagram showing the relationship between thedeployment radius R and projectiles separation Y;

FIG. 11 is a schematic diagram showing the deployment of projectilesfrom the barrel arrays of FIGS. 9B and 9C to a deployment radius 2R;

FIG. 12 is a schematic diagram representing the radial extent of threedimensional projectile fields that could be deployed from a cylindricalmatrix of barrel arrays;

FIGS. 13A to 13C are schematic plan views of the deployment ofprojectiles from the barrel array configuration of FIG. 9A to varyingdeployment radii;

FIGS. 13D to 13F are schematic diagrams of the deployment of projectilesfrom the barrel array configuration of FIG. 9A to produce respectivedeployment patterns;

FIG. 14A is a schematic diagram of a second example of a barrel array;

FIG. 14B is a schematic diagram of a projectile deployment pattern fromthe barrel array of FIG. 14A;

FIGS. 14C to 13E are schematic diagrams of the deployment of projectilesfrom the barrel array configuration of FIGS. 9A and 14A to destroy atarget and decoys;

FIGS. 15A to 15E are schematic diagrams of a support system for mountingthe barrel array of FIG. 3 in a missile;

FIGS. 16A to 16F are schematic diagrams of alternative barrel,projectile and support system configurations;

FIG. 17 is a schematic diagram of a control system for controlling theprojectile deployment;

FIGS. 18A to 18C are schematic plan views of the relative angle ofapproach between the missile of FIG. 2 and a target missile;

FIG. 19 is a schematic diagram of a third example of a barrel array;and,

FIGS. 20A and 20B are a schematic diagram of an example of the use ofbarrel arrays to modify a missile trajectory.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

An example of a kill vehicle suitable for intercepting targets, such asother missiles, will now be described with reference to FIG. 2.

Kill vehicles may come in any one of a number of forms, depending on thecircumstances in which the kill vehicle is to be used. Thus, forexample, the kill vehicle could be adapted to be used above the earth'satmosphere in orbital applications, for example to intercept targetssuch as ICBMs. In this case, the kill vehicle will generally be launchedinto orbit by appropriate rocket systems, such as a missile, or thelike, and then deployed into orbit ready for subsequent use.Alternatively, the kill vehicle may be integrated into a missile,allowing the missile to deploy projectiles, as will be described below.

An example of a typical kill vehicle construction is shown in FIG. 2. Inthis example, the kill vehicle 10 includes a body 11 having a generallycylindrical shape defining a body axis 12. The body generally includes apropulsion system 13 and an associated flight control system 14, whichis adapted to control the trajectory of the kill vehicle in flight, aswill be appreciated by persons skilled in the art. In the example showna shroud is included to provide streamlining for in atmosphere use,although it will be appreciated that this is not required for useoutside an atmosphere.

In use, the kill vehicle is typically propelled towards a target missilewith the trajectory of the kill vehicle being constantly updated by theflight control system 14 in an attempt to directly hit the targetmissile. However, as discussed above, the chance of such a direct hit isminimal and accordingly, in order to increase the chances of the killvehicle 10 disabling the target missile the kill vehicle 10 includesprojectile assemblies for deploying projectiles. The projectiles areadapted to be deployed in a predetermined deployment pattern to therebyincrease the effective collision cross sectional area of the killvehicle 10, thereby increasing the chances of the missile or one of theassociated projectiles hitting the target.

In addition to this, target missiles often deploy sub-munitions,multiple warheads, or decoys, such as chaff or balloons to preventcomplete interception by a kill vehicle. Accordingly, the deployment ofprojectiles in a forward direction by the kill vehicle can allow thedecoys to be cleared prior to an interception, as well as ensuring thatall sub-munitions and warheads are intercepted, as will be described inmore detail below.

In any event, in this example, two sets of projectile assemblies areprovided as shown at 15 and 16, although as will be described in moredetail below, a number of different arrangements could be used.

Irrespective of the number of projectile assemblies, in order to producesuitable projectile deployment patterns, it is preferable to be able tolaunch a large number of projectiles in rapid succession. An example ofa projectile assembly suitable for performing this will now be describedwith reference to FIG. 3.

In particular, FIG. 3 shows a projectile assembly formed from barrel 20having a number of projectiles 21 axially disposed therein. In thisexample, four projectiles 21A, 21B, 21C, 21D are shown, although it willbe appreciated that a larger number of projectiles may be used, and fourare shown for clarity purposes only. The projectiles 21A, . . . 21D areprovided in operative sealing engagement with a bore 23 of the barrel20, such that activation of an associated propellant charge 24A, . . .24D will create a region of high pressure immediately behind therespective projectile 21A, . . . 21D thereby urging the respectiveprojectile out of the barrel 20 in the direction of the arrow 25.

In order to deploy the projectiles 21, a firing system is provided asshown generally at 26.

The firing system typically includes a circuit adapted to generateelectrical pulses, which are then applied via respective connections 27to respective ignition means 28A, . . . 28D. In use, application of anelectrical pulse to a respective one of the ignition means 28A, . . .28D will activate the associated propellant charge 24A, . . . 24D,thereby causing the deployment of the associated projectile 21A, . . .21D.

Accordingly, the firing system 26 is adapted to generate a sequence ofthe pulses which are applied to each of the ignition means 28A, . . .28D in turn, thereby causing the projectiles 21A, . . . 21D to bedeployed from the barrel in sequence. An example of this is shown inFIG. 4.

Barrel assemblies of this type are capable of firing a sequence ofprojectiles at regular intervals whereby a pre-determined distance X maybe established between projectiles in flight, which is useful forproducing the required projectile deployment patterns, as will bedescribed in more detail below.

In this example, the distance X between projectiles 21 fired from thebarrel may be determined solely by the amount of time between theactivation of the successive propellant charges 24. For example, asingle barrel of this type can currently fire at up to 45,000 rounds perminute (RPM), consistent with a separation between projectiles of lessthan 380 mm (15 inches).

In any event, it will be appreciated that a number of variations on theabove mentioned barrel assembly can be provided, as described forexample in the International Patent Applications PCT/AU94/00124(published as WO 94/20809) and PCT/AU96/00459 (published as WO97/04281).

Thus, for example, the projectiles used may be spherical, conventionallyshaped or dart-like, depending on the implementation. For example, dartlike projectiles can be used to provide sealing engagement between thebarrel and the projectiles, thereby allowing the necessary pressure tobe generated by the activation of the respective charge to therebyensure successful deployment.

However, it is possible for the projectiles to be configured so as todefine a cavity between the adjacent projectiles. In this case, thepropellant charge is located in the cavity, such that the high pressureis created in the cavity between the two projectiles. This avoids theneed for the projectiles to seal against the bore of the barrel as thetubular projectiles are adapted to seal nose to tail against one anotheras opposed to the against the barrel bore.

This can be useful in applications in which the barrel is to beconstructed from a material which is susceptible to the high pressuresnormally generated during projectile deployment, as will be explained inmore detail below. As a result, a different configuration of projectileis required as will be described in more detail below.

A further factor is the circumstances in which the projectiles are to beused. For example, in atmosphere applications generally require the useof a streamlined projectile, whereas sub-orbital applications do not.

Atmospheric projectiles may also include fins that generate astabilising spin as the projectile is propelled from a barrel which maybe a smooth-bored barrel.

Alternatively, or additionally the projectiles may be adapted forseating and/or location within circumferential grooves or by annularribs in the bore or in rifling grooves in the bore and may include ametal jacket encasing at least the outer end portion of the projectile.In this case, shaped rifling can be used to impart spin on theprojectiles as they are deployed.

The projectile charge may be form as a solid block to operatively spacethe projectiles in the barrel or the propellant charge may be encased inmetal or other rigid case which may include an ignition means in theform of an embedded primer having external contacts for contacting anpre-positioned electrical contact associated with the barrel. Forexample the primer could be provided with a sprung contact which may beretracted to enable insertion of the cased charge into the barrel and tospring out into a barrel aperture upon alignment with that aperture foroperative contact with its mating barrel contact. If desired the outercase may be consumable or may chemically assist the propellant burn.Furthermore an assembly of stacked and bonded or separate cased chargesand projectiles may be provide for reloading a barrel.

Each projectile may include a projectile head and extension means for atleast partly defining a propellant space. The extension means mayinclude a spacer assembly which extends rearwardly from the projectilehead and abuts an adjacent projectile assembly.

The spacer assembly may extend through the propellant space and theprojectile head whereby compressive loads are transmitted directlythrough abutting adjacent spacer assemblies. In such configurations, thespacer assembly may add support to the extension means that may be athin cylindrical rear portion of the projectile head. Furthermore theextension means may form an operative sealing contact with the bore ofthe barrel to prevent burn leakage past the projectile head.

The spacer assembly may include a rigid collar which extends outwardlyto engage a thin cylindrical rear portion of the malleable projectilehead in operative sealing contact with the bore of the barrel such thataxially compressive loads are transmitted directly between spacerassemblies thereby avoiding deformation of the malleable projectilehead.

Complementary wedging surfaces may be disposed on the spacer assemblyand projectile head respectively whereby the projectile head is urgedinto engagement with the bore 23 of the barrel 20 in response torelative axial compression between the spacer means and the projectilehead. In such arrangement the projectile head and spacer assembly may beloaded into the barrel and there after an axial displacement is causedto ensure good sealing between the projectile head and barrel. Suitablythe extension means is urged into engagement with the bore of thebarrel.

The projectile head may define a tapered aperture at its rearward endinto which is received a complementary tapered spigot disposed on theleading end of the spacer assembly, wherein relative axial movementbetween the projectile head and the complementary tapered spigot causesa radially expanding force to be applied to the projectile head.

The barrel may be non metallic and the bore of the barrel may includerecesses which may fully or partly accommodate the ignition means. Inthis configuration the barrel houses electrical conductors whichfacilitate electrical communication between the control means andignition means. This configuration may be utilised for disposable barrelassemblies which have a limited firing life and the ignition means andcontrol wire or wires therefor can be integrally manufactured with thebarrel.

A barrel assembly may alternatively include ignition apertures in thebarrel and the ignition means are disposed outside the barrel andadjacent the apertures. The barrel may be surrounded by a non metallicouter barrel which may include recesses adapted to accommodate theignition means. The outer barrel may also house electrical conductorswhich facilitate electrical communication between the control means andignition means. The outer barrel may be formed as a laminated plasticsbarrel which may include a printed circuit laminate for the ignitionmeans.

The barrel assembly may have adjacent projectiles that are separatedfrom one another and maintained in spaced apart relationship by locatingmeans separate from the projectiles, and each projectile may include anexpandable sealing means for forming an operative seal with the bore ofthe barrel. The locating means may be the propellant charge betweenadjacent projectiles and the sealing means suitably includes a skirtportion on each projectile which expands outwardly when subject to anin-barrel load. The in-barrel load may be applied during installation ofthe projectiles or after loading such as by tamping to consolidate thecolumn of projectiles and propellant charges or may result from thefiring of an outer projectile and particularly the adjacent outerprojectile.

The rear end of the projectile may include a skirt about an inwardlyreducing recess such as a conical recess or a part-spherical recess orthe like into which the propellant charge portion extends and aboutwhich rearward movement of the projectile will result in radialexpansion of the projectile skirt. This rearward movement may occur byway of compression resulting from a rearward wedging movement of theprojectile along the leading portion of the propellant charge it mayoccur as a result of metal flow from the relatively massive leading partof the projectile to its less massive skirt portion.

Alternatively the projectile may be provided with a rearwardly divergentperipheral sealing flange or collar which is deflected outwardly intosealing engagement with the bore upon rearward movement of theprojectile. Furthermore the sealing may be effected by inserting theprojectiles into a heated barrel which shrinks onto respective sealingportions of the projectiles. The projectile may comprise a relativelyhard mandrel portion located by the propellant charge and whichcooperates with a deformable annular portion may be moulded about themandrel to form a unitary projectile which relies on metal flow betweenthe nose of the projectile and its tail for outward expansion about themandrel portion into sealing engagement with the bore of the barrel.

The projectile assembly may include a rearwardly expanding anvil surfacesupporting a sealing collar thereabout and adapted to be radiallyexpanded into sealing engagement with the barrel bore upon forwardmovement of the projectile through the barrel. In such a configurationit is preferred that the propellant charge have a cylindrical leadingportion which abuts the flat end face of the projectile.

The projectile may be provided with contractible peripheral locatingrings which extend outwardly into annular grooves in the barrel andwhich retract into the projectile upon firing to permit its free passagethrough the barrel.

The electrical ignition for sequentially igniting the propellant chargesof a barrel assembly may preferably include the steps of igniting theleading propellant charge by sending an ignition signal through thestacked projectiles, and causing ignition of the leading propellantcharge to arm the next propellant charge for actuation by the nextignition signal. Suitably all propellant charges inwardly from the endof a loaded barrel are disarmed by the insertion of respectiveinsulating ruses disposed between normally closed electrical contacts.

Ignition of the propellant may be achieved electrically or ignition mayutilise conventional firing pin type methods such as by using acentre-fire primer igniting the outermost projectile and controlledconsequent ignition causing sequential ignition of the propellant chargeof subsequent rounds. This may be achieved by controlled rearwardleakage of combustion gases or controlled burning of fuse columnsextending through the projectiles.

In another form the ignition is electronically controlled withrespective propellant charges being associated with primers which aretriggered by distinctive ignition signals. For example the primers inthe stacked propellant charges may be sequenced for increasing pulsewidth ignition requirements whereby electronic controls may selectivelysend ignition pulses of increasing pulse widths to ignite the propellantcharges sequentially in a selected time order. Preferably however thepropellant charges are ignited by a set pulse width signal and burningof the leading propellant charge arms the next propellant charge foractuation by the next emitted pulse.

Suitably in such embodiments all propellant charges inwardly from theend of a loaded barrel are disarmed by the insertion of respectiveinsulating fuses disposed between insertion of respective insulatingfuses disposed between normally closed electrical contacts, the fusesbeing set to burn to enable the contacts to close upon transmission of asuitable triggering signal and each insulating fuse being open to arespective leading propellant charge for ignition thereby.

A number of projectiles can be fired simultaneously, or in quicksuccession, or in response to repetitive manual actuation of a trigger,for example. In such arrangements the electrical signal may be carriedexternally of the barrel or it may be carried through the superimposedprojectiles which may clip on to one another to continue the electricalcircuit through the barrel, or abut in electrical contact with oneanother. The projectiles may carry the control circuit or they may forma circuit with the barrel.

The projectiles may have reduced propellant loads moving sequentiallytowards the rear of the barrel, in order to maintain a constant muzzlevelocity.

It will therefore be appreciated that a variety of barrel assemblyconfigurations may be used, and specific examples will be described inmore detail below.

In any event, in this example, the sets of projectile assemblies 15, 16can be mounted to the kill vehicle 10 in a variety of configurations inorder to allow a range of projectile deployment patterns to be obtained.For the purpose of example, two main arrangements will now be discussed.

FIG. 5 shows a first example in the form of an arrangement for the firstset of projectile assemblies 15. In particular, the arrangement shown inFIG. 5 is formed from a number of barrels 20 that are circumferentiallyspaced around the body axis 12, and which extend radially outwardly fromthe body axis 12. Accordingly, the barrels form a planar circular array30 which is adapted to deploy projectiles at an angle substantiallynormal to the body axis 12.

An example of this is shown in FIGS. 6A and 6B, which respectively showplan view and end views of the kill vehicle 10, containing a planarbarrel array 30. In this instance, the kill vehicle 10 is showndeploying a line of projectiles 21 from a single barrel 20, as showngenerally at 31. The projectiles 21 are directed so as to strike atarget 32. In this example, the target 32 is shown to be a missile,although it will be appreciated that the target may be of any form, andmay include for example a warhead, sub-munitions, or another killvehicle. For the purposes of description and ease of explanation only,the target will therefore be referred to as a target missile, althoughthis is not intended to be limiting. In any event, as long as theseparation distance X between successive projectiles 21 is less than thecross-sectional diameter D of the enemy missile 32, and as long as thetarget missile 30 passes through the projectile line 31, then at leastone of the projectiles 21 will intercept the target missile 30 as shown.

It will be appreciated by persons skilled in the art that if projectilesare fired from a single barrel 20, then the recoil generated by thisdeployment will impart a reactionary force on the kill vehicle 10 in thedirection shown by the arrow 33. In general, the magnitude of this forcewill be relatively small due to the small size and mass of theprojectiles, and accordingly, the impulse created by the force on thesignificantly greater mass of the kill vehicle will be small. However,this can result in some change in direction of the kill vehicle.

Accordingly, the barrel array 30 is generally arranged with the barrels20 being provided in opposition. As a result, opposing barrels^(201, 202) are generally fired simultaneously, as shown in FIG. 6C,thereby cancelling out the recoil forces on the kill vehicle 10, therebypreventing the kill vehicle being diverted by the deployment of theprojectiles.

It will be appreciated that deploying a single one of the barrels 20 toproduce a single projectile line 31, as shown in FIGS. 6A and 6B, or adual deployment as shown in FIG. 6C, can make it difficult to ensurethat the target missile 32 is hit. In particular, if the barrel 20selected for projectile deployment is not be aligned with the targetmissile 32, then the projectile line 31 and the target missile 32 do notcoincide, as shown in FIG. 6D.

Accordingly, it is typical to deploy projectiles from a number of thebarrels in a single barrel array simultaneously to thereby provide acovering fire over an area, as opposed to along a single line, as shownin FIG. 7, which shows the projectile lines for each of the barrels 20in a single array 30.

As shown in FIG. 8A, in order to guarantee a projectile impacting on atarget missile 32, it is necessary to ensure that the barrel array 30 isconfigured so that the separation distance X between each projectile 21in a projectile line 31, and the separation distance Y betweenrespective projectile lines 31 from adjacent barrels 20, is smaller thanthe diameter D of the target missile 32. Thus:D>X, Y

It should be noted that FIG. 8A shows only three projectile lines 31,and that typically projectiles 21 will be deployed from opposing barrels20 in order to balance the recoil forces, and that more typicallyprojectiles will be deployed from all of the barrels in the array 30simultaneously as described above. This illustration is for examplepurposes only.

In any event, as the barrels 20 face radially outwardly from the killvehicle body axis 12, the distance between each projectile line 31increases further from the kill vehicle 10, such that the first fired orlead projectiles have the greatest separation from one another. It ispossible to define a deployment radius R as the radial distance of thelead projectile from the missile axis 12 when:

-   -   all the projectiles 21 have been fired from the barrels 20 in        the array 30; and,    -   the distance between the kill vehicle 10 and the last deployed        projectile is equal to the separation distance X.

Accordingly, the projectile deployment pattern is generally configuredsuch that the separation distance Y between the lead projectiles 21A ofadjacent projectile lines 31 is less than the missile diameter D whilstall the projectiles 21 lie within the deployment radius R. This ensuresthat the as long as the target missile 32 is within the deploymentradius, it will be hit by at least one projectile.

A single hit is however relatively unlikely, since the target missile 32must pass through a specific point in the deployment pattern whichprovides a ‘gap’ amongst surrounding projectiles as depicted in FIG. 8A.A much more likely scenario is that the target missile 32 will be hit bybetween two and four projectiles, as shown by the target missiles 32A,32B in FIG. 8B. FIG. 8B also highlights that for a projectile deploymentpattern of this form, there is a significantly higher density ofprojectiles near the kill vehicle 10 itself, thereby further increasingthe number of potential hits, as shown by the target missile 32C.

It is also notable that, unlike the prior art, the hits are not merelyfragmentary interceptions, but impacts by projectiles 21 which generallyhave higher mass than fragments. It is also observed that the high speedof the target missile 32, which may be an ICBM or the like, in relationto the projectiles 21, means that the deployed projectile fieldvirtually ‘waits’ for the target missile 32 to pass through the entirearea or volume of the field. (A three dimensional field of projectileswill be described below). For example, the projectiles 21 will typicallymove less than 5 cm for every meter that the target missile 32 moves.This is simply factored into the firing system timing to deploy theprojectiles 21 in accordance with a predetermined deployment pattern aswill be described in more detail below.

In general, the projectile deployment pattern described above can beimproved by providing a number of barrel arrays 30. An example of thiswill now be described with respect to FIGS. 9A, 9B and 9C. In thisexample, a number of barrel arrays 30 are aligned along the missile bodyaxis 12 to form a generally cylindrical matrix 34 of barrel arrays 30.For example, fifty barrel arrays 30 could be stacked together to form acylindrical matrix 34 which would be approximately 750 mm in length.

In this example, the barrels 20 in adjacent arrays 30 can be alignedwith one another.

However, it will be appreciated that an improved area of coverage can beachieved by skewing adjacent barrel arrays 30 with respect to eachother, as shown for example in FIGS. 9B and 9C, which show two adjacentbarrel arrays 30A, 30B, having respective barrels 20A, 20B skewed withrespect to each other, as shown.

FIG. 10 shows that for any two projectile lines at the deploymentdistance R, the two projectile lines are separated by a distance Y, thenat twice the deployment radius R, the projectile lines will be separatedby a distance of 2Y, and so on.

From this it will be appreciated that for barrel arrays 30A, 30B alignedas shown in FIGS. 9B and 9C, this allows a projectile lines 31A, 31B toprovide separation of distance Y at twice the deployment radius 2R ascould be achieved for a single barrel array. An example of this is shownin FIG. 11.

It will be appreciated however, that when the lead projectiles reachtwice deployment radius 2R, the last projectiles will have travelled toa single deployment radius R, as depicted in FIG. 11. Accordingly, athird barrel array 30C will be required to provide projectile lines 31Cto provide coverage within the area defined by a single deploymentradius R. In this case, the lead projectiles 21C, of the third array 30Care desirably timed to be deployed sequentially after the lastprojectiles 21A₆, 21B₆ of the first and second arrays 30A, 30B have beendeployed.

It will be appreciated from this that by combining the projectiledeployment patterns of different barrel arrays in combination, thisallows a range of different areas to be covered by the projectiledeployment pattern. This therefore requires that deployment from each ofthe barrel arrays must be controllable, as will be explained in moredetail below.

In the example shown in FIGS. 9A and 9B, the barrel arrays 30A, 30B areskewed so that the barrels 20B of the array 30B fall between the barrels20A of the array 30A. However, it will be appreciated that this does notneed to be the case. For example, the barrel arrays 30 could be skewedby an amount depending on the number of barrel arrays 30, and the numberof barrels 20 in each array 30. This is performed such that each array30 is skewed by the same amount with respect to each adjacent barrelarray 30 so that the barrels in arrays 30 at each end of the barrelarray matrix 34 are substantially aligned. Thus, the degree of skew canbe linear along the length of the matrix 34.

Alternatively however, barrel arrays 30 may be provided in batches oftwo or three, which are skewed with respect to each other, as describedabove in FIGS. 9B, 9C, with adjacent batches being skewed with respectto each other to thereby provide a further improved field of coverage.It will therefore be appreciated that a range of different degrees ofskewing between adjacent barrel arrays 30, and between adjacent groupsof barrel arrays can be used to provide enhanced coverage of thedeployed projectile pattern.

A further variation is for the barrel arrays 30 to be rotatably mountedto a central support, to allow the barrel arrays to be rotated aroundthe body axis 12 with respect to each other. This allows the projectiledeployment pattern to be modified dynamically before or duringprojectile deployment, to thereby ensure optimum projectile deploymentis obtained, as will be appreciated by persons skilled in the art.

FIG. 12 is a scaled representation of the radial extent of threedimensional projectile fields that could be deployed from a cylindricalmatrix of barrel assemblies, employing multiple skewed circular barrelarrays 30. Distances of up to 12 deployment radii (12R) are shown. Thenumber of circular arrays that would be required in order to deploy toeach radius multiple is shown as table 1 below. TABLE 1 Area covered inNumber of barrel-arrays deployment radii R required 1  1 2  3 3  6 4 105 15 6 21 7 28 8 36 9 45 10  55 11  66 12  78

The list shows that a cylindrical matrix having fifty planar arrays ofbarrel assemblies could deploy a field of projectiles to a distance of9R.

In one example, assuming each barrel 20 includes ten projectiles, andassuming a target missile diameter of 0.5 m, then the deployment radiusR is 5 m. It will be appreciated from this, that use of fifty barrelarrays 30 would provide a deployment radius of approximately 45 m,thereby providing the kill vehicle 10 with an effective impact crosssectional area of about:π(45)²=6360 m²

When compared with the original cross sectional area of the kill vehicle10 (assuming a 0.5 m diameter similar to that of the target missile 32,which gives a cross sectional area of 0.2 m²), it will be appreciatedthat the provision of fifty suitably aligned and controlled barrelarrays 30 can lead to a significant increase in the effectiveinterception cross sectional area of the kill vehicle 10.

However, this example relies on each of the barrel arrays being fired inan appropriate sequence to thereby carpet the entire area between themissile and nine times the deployment radius 9R. In this situation, itwill be appreciated that there will only be a single projectile line 31throughout the area surrounding the missile, as shown for example inFIG. 13A.

In this example, it will be noted that the projectile lines 31 are shownto be laterally displaced with respect to each other at differentdeployment radii distances from the missile. This is due to the forwardmotion of the missile, during the deployment of the projectiles as shownby the arrow 35. In practice, there would be a continuous distributionof the projectiles from the missile, as shown by the dotted line, andthis staggered effect is for clarity only to highlight the differentdeployment radii.

In any event, it will be appreciated from FIG. 13A, there deploying theprojectiles in accordance with this projectile deployment pattern tomaximise the effective cross sectional area of the kill vehicle 10 willresult in the deployed projectiles being effectively only one “plane”deep.

Accordingly, it will be appreciated by persons skilled in the art, thatalternative firing patterns could be selected to maximise the number ofprojectiles nearer to the kill vehicle 10. Thus, for example, the matrixof fifty barrel assemblies 30 could be arranged to deploy projectilesout to a maximum effective radius of 5R, or 25 m in this example.

In this case, Table 1 clarifies that this would leave thirty five barrelassemblies to produce a further projectile deployment pattern. Thus,this could be to produce a second plane of projectiles out to a distanceof 7R, or two further planes of projectiles out to a distance of 5R, asshown for example in FIGS. 13B and 13C respectively. This in turn wouldgreatly increase the probable number of projectile interceptions withinthe radius 5R. Furthermore, the additional planes could be skewed withrespect to each other, thereby further reducing the separation betweenrespective projectile lines 31, as shown for example by the projectilelines 31A, . . . 31F from respective barrel arrays 30A, . . . 30F inFIG. 13D.

Accordingly, it will be appreciated that particular projectiledeployment patterns can be tailored to specific circumstances. Thus, forexample, the projectile deployment pattern can be selected based on therelative positions of the kill vehicle 10 and the target missile 32.Alternatively, the projectile deployment pattern may depend on thenumber and dispersion of any warheads deployed by the target missile 32.Thus, if the target missile 32 has not yet deployed any warheads, thekill vehicle will tend to deploy multiple planes of projectiles toensure a larger number of hits on the target missile 32. However, if anumber of warheads have been deployed, the projectile deployment patternmay be spread over a larger area, to thereby help ensure all thewarheads are intercepted.

The deployment of projectiles from different planar barrel arrays 30 mayalso be separated temporally, meaning that the number of deployed planararrays is not only the divisor as to the distance between adjacent linesof fire (as above), but also as to the distance between projectiles in aline of fire (in end view), as shown for example in FIG. 13E.Accordingly, this option is considered to be advantageous in the eventthat an enemy missile deploys decoy warheads and other fragments.

FIG. 13F illustrates an example in which the barrel arrays are firedsimultaneously to thereby deploy an annular projectile pattern. It willbe appreciated that in this example, in order to maintain the separationY between adjacent projectile lines 31 at the distance of 9R, the numberof barrel arrays required would be nine arrays 30. Thereby providingfurther flexibility over the interception of targets.

Typically local tracking of the trajectory of the target missile 32 ispreferable in order to provide sufficiently flexible fire control,whereby the timing of firing could be adapted to the particularcircumstances encountered by the interception missile. This will bediscussed in more detail below.

A second example of projectile assembly arrangements will now bedescribed. In this example, a number of projectile assemblies in theform of the barrels 20 are mounted as shown generally in FIG. 14A. Inthis example, the barrels are adapted to extended both radiallyoutwardly from and in a direction parallel to the body axis 12. Thus,the barrels 20 effectively form a barrel assembly 40 having a partiallyspherical shape, and which are mounted in the nose of the kill vehicle10 as shown at 16.

In this example, if the kill vehicle is a missile, or the like, which isdeployed in the atmosphere, then it is typical for the barrel array 40to be protected by a shroud 17 in flight, with the shroud being ejectedfrom the body 11 shortly before the projectiles are deployed from thebarrel array 40. However, in the majority of cases in which the killvehicle is deployed outside the earths atmosphere, then there is no needfor a streamlined kill vehicle shape, and the shroud is not required. Inany event, as a result of this configuration, the missile is able todeploy projectiles in advance of the kill vehicle 10, as shown in FIG.14B. In particular, this allows the kill vehicle 10 to deploy asubstantially frustro-concial pattern of projectiles as shown generallyat 41.

This is useful in scenarios in which the target missile 32 deployssub-munitions or decoys, as shown for example in FIG. 14C. In this case,the target missile 32 detects the presence of the kill vehicle 10 andreleases decoys 42, such as balloons or chaff, and optionally one ormore warheads 43, before altering trajectory as shown by the dottedlines, to thereby avoid the kill vehicle 10. Under normal circumstances,this reduces the chance of a successful interception by the kill vehicle10.

Accordingly, the kill vehicle 10 uses the barrel array 40 to deployprojectiles 21 in advance of the kill vehicle 10, as shown by theprojectile lines 41. The projectiles 20 operate to destroy at least thedecoys 42, as shown in FIG. 14D, thereby allowing the kill vehicle todetermine the position of the target missile 32, and any warheads 43.This in turn allows the kill vehicle 10 to either directly intercept thetarget missile 32, and/or warheads 43, or to deploy a predeterminedprojectile pattern, to thereby destroy the target missile 32 andassociated warheads 43, as shown in FIG. 14E.

Thus, the use of the array 40 allows the kill vehicle 10 to destroy anydecoys in the form of balloons, chaff or the like, before the killvehicle 10 itself arrives at the intercept position. The kill vehicle 10can then accurately determine which object is the real target and haveenough remaining time to appropriately react.

Since the projectiles are fired forwardly of the kill vehicle 10, therewould be a resultant rearward force which would tend to slow themissile. However, this may be used to advantage in that the slowing dueto projectile deployment could assist in providing a longer time windowfor a subsequent hit-to-kill intercept by the body of the kill vehicle10.

In any event, deployment of the projectiles is governed by similar rulesto the deployment of the projectiles in the planar array scenariodescribed above with respect to FIGS. 3 to 13, and will not therefore bedescribed in detail. However, it will be appreciated that bymodification of the relative angle between the barrels 20 in the array40 and the body axis 12, this allows a range of spread of projectiles tobe achieved, thereby allowing the relative separation between theprojectile lines 41 to be controlled. This, again allows the barrels tobe fired in sequence to allow a predetermined separation to be obtainedat a predetermined distance from the kill vehicle. This can be used toensure that any decoys or chaff deployed by the target can be destroyedbefore the kill vehicle arrives.

A specific example of implementation of the barrel arrays 30 will now bedescribed. In particular, with the barrels extending radially outwardlyfrom a central axis, it is necessary for the barrels 20 to be mountedsurrounding a central cylinder so that there is sufficient volumeavailable to accommodate the breach ends of the barrels 20. Accordingly,each barrel array 30 would be constructed using a support system, anexample of which is shown in FIGS. 15A and 15C.

As shown the support system 50 includes a central support cylinder 51having a cylinder axis 52. A number of radial connectors 53 extendradially outwardly from the support cylinder 51. The radial connectorsare coupled to circular connectors 54 positioned at respective radii asshown so as to define a conducting mesh plane 56, with a respective meshplane 56 being provided for each barrel array 30 in the matrix 34. Anumber of laterally connectors 55 are also provided.

The connectors are embedded in an insulating material such as thermosetplastic which is moulded to form a cylindrical body forming the barrelarray matrix 34. In use, the barrels 20 are created in the matrix 34 bydrilling cylindrical cavities which extend radially inwardly to thecentral support cylinder. The cavities are aligned so that the barrelsintersect the lateral and circular connectors. Accordingly, the lateraland circular connectors are provided flush with the barrel bore 23, asshown for example in FIG. 15B.

In this configuration, as the lateral connectors 55 are electricallyisolated from the mesh planes 56, it will be appreciated that respectivemesh planes 56 are electrically isolated from other mesh planes in thematrix.

In use, projectiles are inserted into the barrels 20, as shown in FIG.15B. FIG. 15C shows a cross sectional view of the projectiles 21, whichhighlights that each projectile includes a shaped nose and tail portion81, 82. In use the projectiles 21 are inserted into the barrel 20, suchthat the nose and tail portions 81, 82 of adjacent projectiles cooperateto define a cavity for containing the propellant charge 24. The cavityis sealed such that activation of the propellant charge 24 will generatea high pressure in the cavity, thereby urging the lead projectile alongthe barrel 20. It will be appreciated that this avoids the need for theprojectile 21 to seal against the barrel 20, thereby reducing thepressure and heat to which the barrel is exposed. This allows the barrelto be formed from thermoset plastics (or another suitable non-metallic,or other composite material), rather than requiring a more durablematerial.

In addition to this, the tail portion 82 is conductive, and is connectedto the ignition means 28. The projectile also includes a connection 83,which is also connected to the ignition means 28, such as asemi-conductor bridge (SCB), and which is electrically isolated from thetail portion 82 by the insulating band 84. In use, application of asuitable current between the tail portion 82, and connection 83 cantherefore be used to ignite the SCB and thereby activate the propellantcharge 24.

In use, the lateral connectors 55 are adapted to align with theconnection 83, with the circular connectors 54 being aligned with thetail portions 82, as shown in FIG. 15B. This allows the deployment ofthe projectiles 21 to be controlled by suitable control electronicswhich may be completely or partially housed within the central supportcylinder 51. This will typically include at least the firing system 26,which is coupled to the lateral connectors 55 through the use of a PCBextending radially outwardly from the central support cylinder. In thisexample, the PCB can be coupled to the ends of the lateral supportswhich extend radially beyond the radial arms 53, as shown at 55A. Thecontrol electronics will also generally be coupled directly to the meshplanes, which is achieved by having the radial connectors 53 extend intothe central support cylinder 51.

Accordingly, this allows the control electronics, which will bedescribed in more detail below to apply predetermined current to theignition means 28 of selected projectiles of selected barrel arrays byapplying the current to appropriate mesh planes 56 and appropriatelateral connectors 55.

In particular, in order to launch a projectile, the controller will usethe mesh plane as one terminal, thereby allowing any of the projectilesin the respective barrel array to be deployed. The respective one ormore projectiles can then be selected by using the appropriate lateralconnectors 55. Thus, for example, applying a current between theconnector 55A and the mesh plane 56 shown in FIG. 15B, will cause theprojectile 21A to be deployed.

In general a single PCB is provided for the entire matrix 34.Accordingly, the connection 83 extends around each projectile 21, suchthat the portion of the lateral connector 55 on either side of thebarrel 20 is interconnected by the projectile positioned therebetween.An example of this is shown in FIG. 15D, which is a plan view of one ofthe barrels 20. As shown the PCB 58 is coupled to the barrel 20B via theprojectile in the barrel 20A. It will therefore be appreciated that inthis configuration once the projectile is deployed from the barrel 20A,this will effectively break the connection provided by the lateralconnector 55, thereby isolating the barrel 20B from the PCB 58. Thiswould therefore require that the projectiles are launched in sequencefrom the end of the matrix 34 furthest away from the PCB 58, in orderthat remaining projectiles can be deployed.

However, this can be overcome by providing the lateral connector 55 at aposition which only partially intersects the barrels 20, as shown indotted lines. In this case, the lateral connector 55 will remainunbroken when projectiles are deployed from the barrel 20A, therebyallowing projectiles to be subsequently deployed from the barrel 20B, aswill be appreciated by persons skilled in the art.

The connectors can be constructed using thin metal rods (2 mm) cast inpoly-dicyclopentadiene (PDCPD), or another suitable non-metal orcomposite material. The thin metal rods would be manufactured as twoseparate components—in the form of simple rods to form the lateralconnectors 55 and as planes of meshed metal rods to for the mesh-planes56. The planes of meshed metal rods and vertical rods would bepositioned in the cast in similar fashion to the configuration of FIG.15A.

Typically the barrel arrays 30 created in this fashion are skewed withrespect to each other. As a result, the lateral supports will need toextend along the length of the matrix 34 in a curved fashion to ensurethat they intersect the barrels at appropriate positions to therebyallow connections with the projectiles to be achieved.

In one example, the barrel arrays have a radius of 17.3 cm, with thecentral support cylinder having a radius of 4.3 cm, allowing 13 cm forthe length of each barrel 20. Taking into account the propellant charge24 and associated projectile 21, each projectile takes up a length of 2cm, which allows for four projectiles in each barrel, with an additional5 cm of free bore space.

The projectiles are of 0.22 calibre, giving each barrel a diameter of5.6 mm. In addition to this, it is typically necessary to incorporate a0.5 cm spacing between barrel arrays 30, allowing a barrel matrix havingan overall axial length of 31.3 cm to incorporate twenty nine barrelarrays 30.

Furthermore, this configuration allows twenty six barrels to beaccommodated in each barrel array 30 giving an angle between adjacentbarrels of 360/26=13.85 degrees. The base of each barrel would bepositioned 4.3 cm from the support cylinder axis, and taking intoaccount the 0.56 cm diameter of the barrels, provides a 0.48 cm gapbetween adjacent barrels in the barrel array, at the support cylindersurface.

In this configuration, the grid would incorporate twenty six radialconnectors 53, and three circular connectors 54 forming each mesh plane.As there are twenty nine barrel arrays, there would be thirty meshplanes vertically stacked within the missile body. There would also beone hundred and four lateral connectors 55. These would be positionedvertically within the gaps in the mesh planes (as in the above example)and at a slight angle to compensate for the 13.85 degree twist betweentop and bottom mesh plane's. The cylinder would then be cast. Holes toaccommodate the barrels are drilled into the cylinder such that thelands of the rifling are cut into the various metal rods. This is so asthe rods ‘cut’ into the contact surfaces of each barrel as they areinserted.

In this example, the barrels may also be drilled to incorporate rifling,as shown for example in FIG. 15E. In this example, the rifling is in theform of a recess 57 extending into the lateral or circular connectors54, 55, as shown. However, the rifling may alternative be in the form ofa protrusion extending into the barrel 20. In any event, the rifling canbe used to align the projectiles 21 within the barrel 20, as well as toallow spin to be imparted to the projectiles as they are deployed, aswill be appreciated by persons skilled in the art. However this is notessential to the operation of the invention.

Thus, it will be appreciated that this represents a practicalconfiguration that can easily be integrated into existing missiles.However, this is not intended to be restrictive, but rather is only anexample of the configurations that may be used.

It can be shown from simple geometry that the angle of separation Abetween lead projectiles (as measured from the missile axis) atdeployment radius R, is given by:A=2 sin⁻¹ [1/(2P)]

-   -   where P=number of projectiles in the projectile line 31.

Thus, for four projectiles, this gives a separation angle of 14.36°. Inthis example, using twenty six barrels as outlined above, the anglebetween barrels 20 in a barrel array 30 is 360/26=13.85°, therebyallowing the four projectiles to cover the area defined by thedeployment radius.

The actual size of the deployment radius R will depend on the desiredmaximum separation between the projectiles. Thus, for example, if thereis a 1 m separation between projectiles in a projectiles line, thenthere will also be a 1 m separation between lead projectiles 21A inadjacent projectile lines at the deployment radius R which in turn willbe 4 m. The projectiles therefore form a grid in which no twoprojectiles are separated by more than 1 m. If the enemy missile isassumed to be slightly larger than 1 m in diameter then the missilecannot pass through the deployment radius of one barrel-plane without aprojectile interception occurring (and 1-3 further projectileinterceptions being likely).

Assuming 29 barrel arrays mounted to the missile, with appropriateskewing between adjacent barrel arrays (providing a total of 3016projectiles), the grid (in which no two projectiles are separated bymore than the diameter of the enemy missile) can be deployed up to 7deployment radii (which is a radius of 28 m, a diameter of 56 m and anarea of 2462 m² assuming that the projectile separation is set to amaximum 1 m), as outlined above in table 1.

An alternative configuration for assembly of the barrel array matrix 34will now be described. In this example, the barrels are formed asindividual units which are then attached to the central support cylinder51. An example of a suitable barrel 70 is shown in FIG. 16A. In thisexample, the barrel 70 includes a number of projectiles 71 including ashaped tail portion 72, which defines a cavity including the associatedpropellant 74. The propellant is coupled to semi-conductor bridges(SCBs) 75 mounted in inlet ports 76 in the barrel 70 as shown. The SCBsare then coupled to a respective PCB assembly 77 as shown.

Thus, in this example, each barrel is constructed with all theconnections required to couple the projectiles to the controlelectronics. This therefore requires that a respective PCB is providedfor each barrel 20, or at least each barrel array 30, if these areformed concurrently.

The SCBs generally include a header and are threaded into position (orotherwise appropriately held in place) to hold against firing pressure.In this example, the SCBs are held in place by associated plugs, whichare the same size as the inlet ports 76. However the SCB plugs couldextend beyond the outer diameter of the barrel 70 for increasedstrength. The plugs are then connected to a plastic (or other suitablematerial) ‘band’ which is preferably hermetically sealed against thebarrel wall and contains wiring for the four plugs which lead to a mainplug at the rear of the barrel. The ‘band’ could be reinforced with ametal surround for increased strength if deemed required. The main plughas 5 ‘pins’—one four each of the four inlet port plugs containing theSCBs and one earth. The main plug is also preferably hermetically sealedonce attached to firing control system, described in more detail below.

In order to protect the PCB assembly when the barrel 70 is being mountedto a central support cylinder 51, the barrel 70, and PCB may be mountedwithin a cylindrical housing or framework 78 as shown in FIG. 16B. Theframework 78 may be formed from aluminium or a suitable compositematerial as will be appreciated by persons skilled in the art. Theentire structure including the framework 78 can then be attached to thecentral support cylinder 51, to for a matrix similar to that describedabove.

In this example, in order to ensure that the projectiles are locked inplace within the barrel, thereby sealing against the barrel bore, theprojectiles 71 may utilise a wedge portion 71A on the projectile nose asshown in FIG. 16C. In this case, when the propellant and projectiles areinserted into the barrel in the direction of arrows 73, the projectilescan be urged in towards the breach end of the barrel 70, thereby causingthe wedge shaped portion to seal against the barrel bore. Similarly,when any particular projectile is fired the force from the associatedpropellant expansion further locks the next projectile in the stackagainst the barrel wall, thereby preventing the blow-by ignition ofsuccessive rounds in the stack.

However, in this example, the tail portion 72 must be of a relativelylarge thickness to provide necessary support during the deployment ofthe projectiles. Accordingly, an alternative configuration can be usedas shown for example in FIG. 16D. In this example, projectiles 71 aretubular. This provides additional strength whilst utilising a smallervolume of material to thereby provide for an increased propellant volumein a projectile of the same length. The projectile 71 can includeportions 79 in the form of holes or ‘soft spots’, which allow theignition of the SCB to ignite the propellant by burning through thissection upon ignition. If the portions 79 are simply to be holes, thepropellant cavity of each projectile would be filled with propellantthrough the inlet ports once the projectiles have been loaded and lockedinto position in the barrel. The SCB and header plugs would then bethreaded into position. If the portions 79 are ‘soft spots’ theprojectiles would be filled with propellant before insertion into thebarrel.

This type of projectile also utilises sealing against the barrel wallboth in construction and as a result of the propellant expansion of theround in front to prevent the blow-by ignition of successive rounds inthe stack, as shown in FIG. 16E.

An example of the mounting of the barrels 20 of FIGS. 16D and 16E isshown in FIG. 16F, which is an end view of the matrix 34, with thecylindrical nature of the construction, and the relative angles betweenthe barrels 70 not being shown for clarity. In any event, in thisexample, the framework 78 is formed from a central support cylinder 78A,equivalent to the central support cylinder 51 of the embodiment shown inFIG. 15, which therefore incorporates the control electronics. Theframework 78 further includes an inner cylinder 78B and an outercylinder 78C. In use, the cylinders are held in position by respectivevertical supports (not shown).

The matrix is therefore constructed by first coupling the inner andouter cylinders 78B, 78C to the central support cylinder 78A using theappropriate vertical supports. A hole is then drilled through the outerand inner cylinders 78B, 78C, as shown at 78E, 78F, with the drillingbeing continued through into the central support cylinder 78A, to definea recess 78D. The barrels 70 can then be inserted into the respectiveholes, such that the barrels 70 are supported by the respective innerand outer cylinders 78B, 78C, with the breach end of the barrels 70resting in the recess 78D created in the central support cylinder.Typically however, before the barrel is inserted, an additional hole isdrilled though all of the central support cylinder 78A, and the innerand out cylinders 78B, 78C to incorporate the PCB 77. In particular,this is arranged such that the PCB extends through the central supportcylinder 78A, allowing the PCB to be coupled to the control electronics,thereby allowing the barrels 70 to be inserted into the holes 78E, 78F,with the breach end in the recess 78D, and the PCB extending into thecavity within the central support cylinder 78A.

It will be appreciated by persons skilled in the art that this allowsthe framework to be constructed and the barrels 70 simply insertedtherein. The barrels can be held in place using an appropriate retainingmeans depending on the application and the stress to which the matrix 34will be subject. Thus for example, the barrels 70 may be held in placedue to a tight fit between the breach end and the recess 78D, oralternatively may be held in place using glue, welding, screws or thelike.

In any event, the insertion of the barrels also allows the PCBs 77 to bealigned with appropriate connectors provided on the control electronics,thereby ensuring that insertion of the barrels 70 into the framework 78also automatically couples the barrel to the control electronics,thereby simplifying the process of producing the matrix 34.

The control electronics which form the firing system typically include acircuit adapted to generate pulses of electricity which are applied tothe ignition means 18, 75. This can be achieved using a hard-wiredignition system constructed using either metal barrels to act as one ofthe required connections to the ignition means, or through use ofbarrels cast from reaction injection moulded (RIM) thermo-set PDCPD,with wires embedded therein. In either case, the ignition means aregenerally in the form of SCBs as described above.

In the above mentioned case, it is possible to provide a respectiveconnection to each ignition means in each barrel within an array.Alternatively it is also possible to utilise a two-wire ignition systemin which the mesh planes 52 and lateral supports 55 would be replacedwith a single loop of wire spanning either side of each barrel in theentire system. Selective ignition would be based upon coded SCBs orthrough the utilisation of varying resistances for different ignitionmeans 18. In this case, the firing system would be adapted to generatecoded pulses, or pulses having different current magnitudes.

An example of the control systems will now be described in more detailwith respect to FIG. 17. In particular, the control system willtypically be formed from a processing system 60 coupled to a number ofsensors 61, and the firing systems 26. In use the processing system willtypically include a processor 65, coupled to a memory 66, an optionalI/O device 67, and an external interface 68, via a bus 69.

In use, the sensors are used to provide signals representative of theposition of the target missile relative to the kill vehicle 10. Theprocessor 65 obtains signals from the sensors 61, and then uses these toselect a projectile deployment pattern in accordance with pattern datastored in the memory 66. The processor 65 then generates suitablesignals to thereby activate the firing systems 26, and deploy theprojectiles as required. In this case, a respective firing system 26 maybe provided for each barrel, or each barrel array 30. However, typicallya single firing system will be provided for all the barrel arrays 30.For example, in the case of the barrel matrix 34 shown in FIGS. 15A-D,the firing circuit will typically consist of a circuit for generating asuitable electrical pulse for activating the ignition means, togetherwith a switching system for selectively coupling the output of thefiring circuit to respective ones of the mesh planes 56 and the lateralconnectors 55, as required. In any case, the one or more firing systems26 must be adapted to deploy the projectiles independently from eachbarrel 20 of each barrel array 30.

In any event, it will be appreciated from this that the control systemcan be implemented in a number of ways. For example, the control systemcan be adapted to receive signals from the sensors 61 mounted to themissiles 10.

Typically in this case the sensors 61 would include an array of sensorytechnology that can be used to detect the presence of the targetmissile, and optionally guide the kill vehicle 10 to intercept thetarget missile. As will be appreciated by persons skilled in the art,such technologies are often deemed classified, and as a result, detailis not provided in this document. However, examples of sensorytechnologies used in the detection of target missiles and the guidanceof kill vehicles 10 include (but are not limited to):

-   -   EMR (electromagnetic radiation) reflection analysis sensors,        such as radar, X-ray or infra-red sensors    -   Particle reflection analysis sensors

In any event, the sensors are typically mounted to the front of the killvehicle to detect targets in front of the kill vehicle.

However, remote sensing may also be used, in which case, the sensors maybe in the form of satellites, adapted to sense the position of both thekill vehicle 10 and the target missile 32. In this case, an indicationof the respective missile positions can be transferred to the processingsystem 60 via an appropriate wireless communications system, as will beappreciated by persons skilled in the art.

Alternatively, the processing system 60 may be positioned remotely tothe missile. For example the processing system 60 may be located in asatellite, in a ground based base station, such as a command centre orthe like. The processing system 60 would be adapted to activate thefiring system 26 via an appropriate wireless communications system.

In either case, the processing system 60 will be adapted to determinethe relative positions of the missiles and then access pattern datastored in the memory 66. This may be in the form of a Look-Up Table(LUT), which specifies the optimum projectile deployment pattern thatshould be used to maximise the chances of destroying the target missile.

In particular, the LUT will specify from which barrels 20 and whichbarrel arrays 30 projectiles are to be deployed for different sizes andintercept courses for the target missile 32. It will be appreciated thatthis may be in the form of commands for controlling the switching tothereby control the connection between a firing circuit and selectedones of the mesh planes 56 and lateral connectors 55.

Thus, in general, the processor 65 will determine the likely velocity ofthe target missile at interception and then taking into account the typeof missile, select an appropriate projectile deployment pattern. Forexample, the cross sectional area of the target missile will be used todetermine the maximum separation distance X between projectiles, andhence the deployment radius R and the associated rate of deployment ofthe projectiles. Similarly, the relative positioning and velocity of thetarget missile will result in modification of the projectilepositioning.

The processing system 60 will then determine the time at which theinterception is to occur, and time the deployment of the projectiles 21accordingly.

It will also be appreciated from the above that the processing system 60may form part of the flight control system 14 adapted to control themissile trajectory.

Some examples will now be described with respect to FIGS. 18A to 18Cwhich show that the optimum angle of approach is 0-degrees (or180-degrees relative to one another) because the effective width of theprojectile field is maximised, as shown in FIG. 18A. An approach angleof 90-degrees the advantages of the missile system are largely lost. Atacute angles of approach, as depicted in FIG. 18B, the extent ofcoverage of the projectile lines 31 are geometrically reduced to asmaller effective size, as shown in the dotted line in FIG. 18B, therebyreducing the effectiveness of the system.

Thus, it will be appreciated that if the missiles are approaching with aless than optimum angle, the processing system 60 will select thelargest size projectile deployment pattern (ie. the one extending to thelargest number of deployment radii) available to thereby maximise achance of the target missile being successfully intercepted. However, ifthe missile is approaching at a more optimum angle, the processingsystem 60 may reduce the number of deployment radii to which theprojectiles will extend with the required separation distance to therebymaximise the number of hits against the missile that will be achieved.

Thus, there may be situations however, in which the grid is not requiredto be deployed to the maximum radius. In these situations the grid canbe deployed to a smaller number of deployment radii, ensuring multipleprojectile interceptions within the chosen radius.

For example, with 29 projectile arrays 30, table 1 indicates that if thegrid is only deployed to 3 deployment radii, 7 barrel planes would berequired with 22 left over. The left over barrel-planes can be used toblanket the required radius with multiple sets of grids (in which no 2projectiles are separated by more than the diameter of the enemymissile).

It can be seen from the above table that at 3 deployment radii, 4 setsof grids can be deployed (thus ensuring at least 4 projectileinterceptions with 1-12 further projectile interceptions being likely)with 1 barrel-plane left over. This relationship is summarised in thetable 2 below: TABLE 2 Number of expected Number Distance projectileinterceptions. Distance between of likely covered in ie. the number oflines/projectiles further deployment complete projectile-grids in enemymissile projectile radii R covering the radius diameters interceptions 129  1/29 1-87 2 9 1/9 1-27 3 4 1/4 1-12 4 2(.6) 1/2 1-6  5 1(.8) 1 1-3 

In the case, each barrel array would be skewed by 13.85/29=0.48 degreesas to one another (in a ‘twisting’ fashion from top to bottom). Thismeans that (for example) if the grid (using all of the 29 barrel-planesavailable) is only deployed to one deployment radius, the distancebetween any two projectile lines in the grid is no more than 1/29 enemymissile diameter.

Similarly in this scenario, firing could be timed such that theprojectiles in each line from any particular barrel-plane would be fired1/29 of an enemy missile diameter later’ than each adjacentbarrel-plane, in sequential fashion. This means that if enemy missilediameter is set to 1 m (deployment radius therefore being 4 m), anyobject larger than 3.4 cm diameter cannot pass through the grid withoutintercepting at least 29 projectiles (with 1-87 further projectileinterceptions being likely).

The barrel-plane cylinder could also deploy projectiles in a ‘ring’shape such that at 7 deployment radii (7×4 m) for example, the distancebetween projectiles is only 25 cm.

The ring would have a depth of 4 enemy missile diameters and could bedeployed up to 28 deployment radii and maintain a grid in which no 2projectiles are separated by more than enemy missile diameter.

This relationship is summarised in table 3 below. TABLE 3 Number ofDistance ring is Number of Distance between likely further deployed toin expected projectile lines in enemy projectile deployment radiiinterceptions missile diameters interceptions 1 29  1/29 1-87 2 14  1/14 1-42 3 9 1/9 1-27 4 7 1/7 1-21 5 5(.8) 1/5 1-15 6 4(.8) 1/4 1-12 74 1/4 1-12 8 3(.6) 1/3 1-9  9 3(.2) 1/3 1-9  10  2(.9) 1/2 1-6  11 2(.6) 1/2 1-6  12  2(.4) 1/2 1-6 

It will therefore be appreciated that the control system can select arespective one of the firing patterns outlined above, as well asvariations thereon, in order to maximise the chance of successfullydisabling the target missile, and any deployed sub-munitions.

When controlling the projectile deployment pattern for a missile systemsuch as that described above, it is also useful to take into account anumber of additional factors, such as:

-   -   Recoil: The system is designed so as each barrel has a parallel        and aligned barrel facing in the opposite direction. If both        barrels fire simultaneously recoil forces will cancel out and        there will be no resultant change in the trajectory of the kill        vehicle.    -   Muzzle velocity: The muzzle velocity can be tailored to meet        specific requirements by varying the propellant load carried        within each projectile.    -   Dispersion: The projectiles will tend to naturally disperse due        to small natural variations in trajectory.

In the configuration described above, the total weight of the supportsystem, barrels and projectiles is under 50 kg, thereby allowing theassembly to be mounted to existing missiles/kill vehicles.

It will be appreciated by persons skilled in the art that a number ofdifferent barrel arrays can be used. Thus, for example, a barrel arraycould be used to deploy projectiles in front of the kill vehicle 10, inwhich case the operation of the control system is adapted accordingly.Such a configuration is useful for destroying sub-munitions(decoys/balloons) ejected in front of the main target missile, as wellas in for providing additional opportunity for a successful hit on themissile itself, as described above with respect to FIGS. 14A to 14E.

An example configuration will now be described. For example, assumingthe muzzle velocity of the .22 cal projectiles is 300 m/s and thevelocity of the enemy missile relative to the kill vehicle 10 is 7,000m/s. This provides a closing velocity of 7,300 m/s. Now, in order thatthe missile has ten seconds (example time period) to manoeuvre afterprojectile impact, the projectile grid must be fired when the killvehicle 10 is 7.3×10=73 km from the enemy missile. Using this distance,we can calculate what angle between the forward-facing barrels providesan appropriate projectile pattern at this distance. In this example, theseparation angle A between projectiles is given by:—tan(A)=1/7300.A=tan−1 (1/7300)=0.0078 degrees.

It will be taken throughout this document that such an angle isnegligible when considering the design aspects of the system, andaccordingly, it can assumed that the barrel array is a cylinder, withcircumferentially spaced barrels extending parallel to the missile bodyaxis 12, as shown in FIG. 19. Assuming a volume of 32.3 cm in diameterand 31 cm in depth, to allow the barrel array to be mounted in astandard missile, it is possible to determine the total number ofprojectiles that can be provided.

In particular, a cuboid of these dimensions could include 30 barrelswith 31, 0.5 cm spacings in between and on either edge takes up(30×0.56)+(31×0.5)=32.3 cm. This gives us a total of 30×30=900 barrels.The area of the leading face of the cuboid=32.3×32.3=1043 cm2. The areaof a circle of this diameter is (pi)(16.15)2=819 cm2. Thusproportionally, the cylinder would comprise (819/1043)×900=707 barrels.

A central support cylinder 51 is generally provided to house theprocessing system 60 and other appropriate electronics. A cuboid ofthese dimensions would house approx 5×5=25 barrels. The area a square ofthese dimensions is 25 cm² and a circle of these dimensions 20 cm².Subtracting 20 barrels from the previous total of 707 to come to the endresult of approximately 687 barrels. Subtracting 5 cm of free bore and 2cm of space at the base of the barrels there is 24 cm of barrel left tohold projectiles—12 projectiles per barrel. There are thus 687×12=8244projectiles in the barrel array.

Upon first impact the projectile grid would be 30 m in diameter with a 1m separation between lead projectiles. The natural inherent dispersionbetween projectiles from the same barrel would reduce this distance to astatistically appropriate average.

The configuration can be built using a grid system of radial, circularand lateral connectors, similar to that shown in FIGS. 15A and 15B. Inthis case, the barrels are inserted in a direction parallel to thesupport body axis. Accordingly, in this case, circular connectors, wouldbe electrically coupled to lateral connectors to define cylindrical meshplanes. The barrels 20 would intersect the circular connectors to allowa mesh plane to be connected to each of a group of circumferentiallyspaced barrels 20 at a respective radial position. A number of meshplanes having respective radii would be provided to allow all thebarrels to be coupled to a mesh plane. Radial connectors, which areelectrically isolated from the mesh planes, would then be coupled torespective projectiles 21 in the barrels. In a manner similar to thatdescribed above, this allow control electronics to be independentlycoupled to each projectile in the array, allowing the respectiveprojectiles to be deployed independently, as will be appreciated bypersons skilled in the art. Thus, this allows a matrix to be formed bydrilling appropriate barrels in a direction parallel to the body axis.

Again, the total weight of such a system will be under 50 kg.

Alternatively, the barrel array 40 may be formed by mounting barrels,such as the barrels shown in FIG. 16 to a central support of some form.Again, the exact form of this will depend on the relative orientationsof the barrels 20 within the array 40, but will typically include usinga number of substantially planar support planes, aligned substantiallyperpendicularly to the body axis 12. Holes can then be drilled throughthe support planes in a direction substantially parallel to the bodyaxis 12, thereby allowing the barrels to be inserted therein.

In this example, it will be appreciated that if the barrel are similarto the barrels 70, then the barrels may include a PCB 77 which isadapted to connect the barrel to the control electronics. The manner inwhich this is achieved will depend on the implementation. Fr example,the barrel array may use a substantially planar support into which thebreach ends of the barrels are provided, with the control electronicsbeing housed in an appropriate cavity on the underside of the planarsupport. In this case, the PCBs can then be adapted to be insertedthrough suitable holes in the planar support, to interface directly withappropriate connectors on the control electronics.

Alternatively, for example, the control electronics can be housed in acentral support cylinder, provided along the body axis. In this case,the barrels are circumferentially spaced around the central supportcylinder, and it is therefore necessary to connect the PCBs 77 to thecontrol electronics using additional connections. This, may be achievedfor example by having appropriate connections, such as a purpose builtPCB extending along the planar supports, to the control electronics inthe central support cylinder, as will be appreciated by persons skilledin the art.

A further example of use of the barrel arrays will now be described withrespect to FIGS. 20A and 20B. In particular, in this example, theprojectiles are deployed in a non symmetrical fashion, to therebyfunction as a divert propulsion system to effect changes to thetrajectory of the kill vehicle 10. Thus, for example, deployingprojectiles along the projectile lines 31 will impart a lateral momentumto the kill vehicle. Assuming the kill vehicle has an existing forwardmomentum, then the position of the missile following this manoeuvre willbe as shown in the dotted lines.

In this example, the kill vehicle includes a set of barrel arrays 15A inthe tail portion of the kill vehicle in order to allow additionalmodification of the kill vehicle's momentum, as will be appreciated bypersons skilled in the art.

In general, the firing of a single line of projectiles 31 from thebarrel array 30, and another line of projectiles 31A from the barrelarray 30A, will only impart a minimal momentum change on the killvehicle, and accordingly, it is typical for a number of projectile lines31, 31A to be deployed, to thereby increase the change in momentum onthe kill vehicle 10, as will be appreciated by persons skilled in theart.

It will therefore be appreciated that a wide range of configurations canbe used, and that any number of barrel arrays of different designs maybe incorporated into a missile in a manner similar to that describedabove. Appropriate control of the projectile deployment by theprocessing system 60 can then be used to deploy the projectiles in apredetermined pattern, thereby increasing the likelihood of disabling atarget missile.

It will be appreciated that the kill vehicle 10 can also be used tointercept other targets, including both static and moving targets. Inthis case, the projectile deployment pattern can be adapted depending onthe respective target. Thus, for example, the deployment pattern may bespread out over a wide area, or concentrated, to thereby maximise damageto a target, or to allow multiple targets to be hit simultaneously,using a single kill vehicle 10.

It will also be appreciated that the barrel arrays could be mounted tovehicles other than kill vehicles, depending on the circumstances inwhich they are to be used. Thus, for example, the barrel arrays could bemounted directly to missiles, or the like. The use of the term killvehicle throughout the specification is therefore by way of exampleonly, and it will be appreciated that the projectile deployment systemcould be mounted to and implemented on any device. Thus, the projectiledeployment system may be integrated into any target intercept device.

Preferably the target intercept device is however propelled, with thedevice being propelled primarily in a forward direction substantiallyparallel to the body axis, as will be appreciated by persons skilled inthe art, and as described above, although this is not essential.

It will be noted that the target missile will impact on the projectileswith a relative velocity of up to and beyond Mach 23. In this case,deployment of a homogenous, grid-like field of projectiles, in which allprojectiles are separated by slightly less than the cross-sectionaldiameter of the target missile, ensures that the target missile willimpact on at least some of the projectiles in the field.

Persons skilled in the art will appreciate that numerous variations andmodifications will become apparent. All such variations andmodifications which become apparent to persons skilled in the art,should be considered to fall within the spirit and scope that theinvention broadly appearing before described.

1. A projectile deployment system for use in a target interceptingdevice, the projectile deployment system including: a) A body defining abody axis; b) A barrel array formed from a number of barrelscircumferentially spaced around the body axis, each barrel beingarranged at a predetermined angle with respect to the body axis; c) Anumber of projectiles axially stacked along each barrel; d) A number ofcharges, each charge being associated with a respective projectile tourge the respective projectile along the barrel upon activation tothereby deploy the projectile.
 2. A projectile deployment systemaccording to claim 1, wherein: a) The body includes a support bodydefining the number of barrels, the barrels being adapted to receive theprojectiles and associated charges at predetermined positions; and, b)The body including a number of connectors extending therethrough forconnecting first and second connections provided on each projectile to acontroller.
 3. A projectile deployment system according to claim 2, thecontroller being housed in a cavity in the support body.
 4. A projectiledeployment system according to claim 2, the first and second connectionsof each projectile being coupled to an ignition means for activating thecharge associated with the respective projectile.
 5. A projectiledeployment system according to claim 2, the connectors including: a) Anumber of sets of first connectors, each set of first connectorscoupling the first connections of each of the projectiles in arespective set of barrels to the controller; and, b) A number of secondconnectors, each second connector coupling the second connections ofselected projectiles in different sets of barrels to the controller,thereby allowing the controller to apply activation signals to selectedones of the sets of first connectors and the second connectors tothereby deploy selected projectiles.
 6. A projectile deployment systemaccording to claim 1, the body including a support member having anumber of barrels mounted thereon.
 7. A projectile deployment systemaccording to claim 6, wherein: a) Each projectile is associated withignition means for activating the charge associated with the respectiveprojectile; b) Each barrel is provided with respective barrel connectorsfor connecting to the ignition means, the connectors extending along thebarrel to a breach end; and, c) A number of connectors provided in thesupport member, the connectors being adapted to cooperate with thebarrel connectors to thereby couple the ignition means to a controller.8. A projectile deployment system according to claim 7, the supportmember including a cavity for receiving the controller.
 9. A projectiledeployment system according to claim 1, the projectile deployment systemincluding a controller for deploying the projectiles by: a) Activatingthe charge associated with the projectile positioned nearest to a muzzleend of one or more selected barrels; b) Repeating step (a) to therebyfire the projectiles sequentially from the barrel.
 10. A projectiledeployment system according to claim 9, the controller being adapted toselectively activate the charges to thereby deploy the projectiles inaccordance with a projectile deployment pattern.
 11. A projectiledeployment system according to claim 10, the controller activating thecharges by applying a predetermined activation pulse thereto.
 12. Aprojectile deployment system according to claim 11, the projectiledeployment system including one or more firing circuits for generatingthe activation pulses.
 13. A projectile deployment system according toclaim 10, the controller being adapted to fire the charges atpredetermined time intervals to thereby control the rate of deploymentof the projectiles.
 14. A projectile deployment system according toclaim 1, the controller including: a) A store for storing pattern datarepresenting one or more predetermined projectile deployment patterns;and, b) A processor adapted to: i) Determine the position of the targetwith respect to the projectile deployment system; ii) Select aprojectile deployment pattern in accordance with position of the target;and, iii) Selectively activate the charges in accordance with thepattern data.
 15. A projectile deployment system according to claim 14,the projectile deployment system including one or more sensors forsensing the target, the processor being adapted to monitor the sensorsto thereby determine the position of the target with respect to theprojectile deployment system.
 16. A projectile deployment systemaccording to claim 15, the controller being coupled to a remote sensingsystem via a communications system, the remote sensing system beingadapted to; a) Determine the position of the target with respect to theprojectile deployment system; and, b) Transfer an indication of thetarget position to the controller via the communications system.
 17. Aprojectile deployment system according to claim 14, the pattern dataindicating at least one of: a) The barrels from which projectiles shouldbe fired; and, b) The rate of deployment of the projectiles.
 18. Aprojectile deployment system according to claim 1, at least some of thebarrels extending radially outwardly from the body axis.
 19. Aprojectile deployment system according to claim 18, the projectiledeployment system including at least one planar barrel array, the planarbarrel array including a number of barrels extending radially outwardlyfrom the body axis so as to define a plane perpendicular to the bodyaxis.
 20. A projectile deployment system according to claim 19, theprojectile deployment system including a number of planar barrel arraysspaced apart along the body axis.
 21. A projectile deployment systemaccording to claim 20, at least some of the planar barrel arrays beingskewed with respect to each other such that at least one of the planarbarrel arrays deploys projectiles In a direction different to at leastone other planar barrel array.
 22. A projectile deployment systemaccording to claim 21, the barrels of adjacent barrel arrays beingpartially interleaved.
 23. A projectile deployment system according toclaim 20, one or more of the planar barrel arrays being rotatablymounted to the body to thereby rotate about the body axis.
 24. Aprojectile deployment system according to claim 1, at least some of thebarrels extending in a direction parallel to the body axis.
 25. Aprojectile deployment system according to claim 24, at least some of thebarrels defining a barrel array for deploying projectiles in directionsalong and outwardly from the body axis.
 26. A projectile deploymentsystem according to claim 1, the projectile target intercepting devicebeing a kill vehicle, the kill vehicle including; a) A propellant systemfor propelling the kill vehicle; and, b) A flight controller, the flightcontroller being adapted to control the propellant system to therebycontrol the kill vehicle trajectory.
 27. A projectile deployment systemaccording to claim 26, the propellant system being adapted to bepropelled in a direction substantially parallel to the body axis.
 28. Aprojectile deployment system according to claim 1, the projectile targetintercepting device being a missile.
 29. A method of manufacturing aprojectile deployment system, the method including: a) Providing a bodymember defining a body axis; b) Providing a support material surroundingthe body member, the support material including a number of first andsecond connectors embedded therein; c) Drilling a number of holes in thesupport material to thereby define one or more barrels, the barrelsbeing circumferentially spaced around the body axis and being adapted tointersect selected ones of the first and second sets of connectors; and,d) Inserting projectiles and associated charges into the barrels, theprojectiles including first and second connections, the projectilesbeing aligned such that: i) The first connections of each of theprojectiles in a respective set of barrels are coupled to a respectiveset of first connectors; and, ii) The second connections of respectiveprojectiles in different sets of barrels are coupled to respectivesecond connections.
 30. A method according to claim 29, the methodincluding: a) Mounting a control system within a cavity in the bodymember; and, b) Coupling the control system to the sets of firstconnectors and the second connectors.
 31. A method according to claim29, the method including manufacturing a projectile deployment systemincluding: a) A body defining a body axis; b) A barrel array formed froma number of barrels circumferentially spaced around the body axis, eachbarrel being arranged at a predetermined angle with respect to the bodyaxis; c) A number of projectiles axially stacked along each barrel; d) Anumber of charges, each charge being associated with a respectiveprojectile to urge the respective projectile along the barrel uponactivation to thereby deploy the projectile.
 32. A method ofmanufacturing a projectile deployment system, the method including: a)Providing a body member defining a body axis; b) Coupling a barrel arrayhaving a number of barrels to the body member, the barrels beingcircumferentially spaced around the support axis, and each barrel beingarranged at a predetermined angle with respect to the body axis; thebarrels including a number of connectors; c) Inserting projectiles andassociated charges into the barrels, the projectiles including first andsecond connections adapted to be aligned with respective ones of thenumber of connectors; and, d) Mounting a control system in a cavity inthe barrel array, the control system being coupled to the connectors toallow the projectiles to be deployed.
 33. A method according to claim32, the method including manufacturing a projectile deployment systemincluding: a) A body defining a body axis; b) A barrel array formed froma number of barrels circumferentially spaced around the body axis, eachbarrel being arranged at a predetermined angle with respect to the bodyaxis; c) A number of projectiles axially stacked along each barrel; d) Anumber of charges, each charge being associated with a respectiveprojectile to urge the respective projectile along the barrel uponactivation to thereby deploy the projectile.
 34. Apparatus forintercepting a target, the apparatus including: a) A projectiledeployment system having: i) A body; and, ii) A number of projectilesystems mounted to the body in an array, each projectile system beingadapted to deploy a number of projectiles in a predetermined directionwith respect to the body and, including: (1) a barrel (2) a number ofprojectiles (3) a number of charges, each charge being adapted to urge arespective projectile along the barrel to thereby deploy the projectile;b) A controller, the controller being adapted to selectively activateone or more of the projectile systems to thereby deploy projectiles inaccordance with a projectile deployment pattern.
 35. Apparatus accordingto claim 34, the apparatus including: a) A vehicle having a vehicle bodydefining a vehicle axis; b) A propellant system for propelling thevehicle; and, c) A flight controller, the flight controller beingadapted to control the propellant system to thereby control the vehicletrajectory.
 36. Apparatus according to claim 34, the apparatus includinga projectile deployment system including: a) A body defining a bodyaxis; b) A barrel array formed from a number of barrelscircumferentially spaced around the body axis, each barrel beingarranged at a predetermined angle with respect to the body axis; c) Anumber of projectiles axially stacked along each barrel; d) A number ofcharges, each charge being associated with a respective projectile tourge the respective projectile along the barrel upon activation tothereby deploy the projectile.
 37. Apparatus according to claim 36, theprojectile deployment system being aligned such that the vehicle axis issubstantially coaxial with the body axis.
 38. Apparatus according toclaim 36, the deployment of each projectile causing a reactive forcealong the respective barrel, the pattern of projectiles being at leastone of: a) Symmetric around the body axis to thereby equalise thereactive forces on the body; and, b) Non-symmetric around the body axisto thereby generate non-symmetric reactive forces, thereby causingdeflection of the body.
 39. Apparatus according to claim 38, the firingpattern of the projectiles being adapted to control the trajectory ofthe vehicle.
 40. Apparatus according to claim 34, the target being amissile.
 41. Apparatus according to claim 34, the projectile deploymentpattern being selected to thereby increase the effective cross sectionalarea of the vehicle.
 42. Apparatus according to claim 34, the controllerincluding: a) One or more sensors for sensing the target; and, b) Aprocessor adapted to: i) Monitor the sensors to thereby determine theposition of the target with respect to the missile; ii) Determine aprojectile deployment pattern; iii) Select one or more of the projectilesystems in accordance with the projectile deployment pattern; and, iv)Activate the selected projectile systems.
 43. Apparatus according toclaim 42, the controller including a store for storing pattern datarepresenting a number of different projectile deployment patterns, theprocessor being adapted to select one of the stored projectiledeployment patterns in accordance with the position of the target. 44.Apparatus according to claim 34, the vehicle being at least one of akill vehicle and a missile.
 45. A missile for intercepting a target, themissile including: a) A missile body defining a missile axis; and, b)Apparatus including: c) A projectile deployment system having: i) Abody; and, iii) A number of projectile systems mounted to the body in anarray, each projectile system being adapted to deploy a number ofprojectiles in a predetermined direction with respect to the body and,including: (1) a barrel (2) a number of projectiles (3) a number ofcharges, each charge being adapted to urge a respective projectile alongthe barrel to thereby deploy the projectile; b) A controller, thecontroller being adapted to selectively activate one or more of theprojectile systems to thereby deploy projectiles in accordance with aprojectile deployment pattern.
 46. A method of intercepting targets, themethod including: a) Launching a device at the target, the deviceincluding: i) A body; and, ii) A number of projectile systems mounted tothe body in an array, each projectile system being adapted to deploy anumber of projectiles in a predetermined direction with respect to thebody and, including: (1) a barrel (2) a number of projectiles (3) anumber of charges, each charge being adapted to urge a respectiveprojectile along the barrel to thereby deploy the projectile; b)Selectively activating one or more of the charges to thereby deployprojectiles in accordance with a projectile deployment pattern such thatat least one of the projectiles intercepts the target.
 47. A methodaccording to claim 46, the method including: a) Determining the positionof the target with respect to the device; b) Select a projectiledeployment pattern in accordance with position of the target; and, c)Activating the projectile systems in accordance with the selectedprojectile deployment pattern.
 48. A method according to claim 47, eachprojectile system including: a) A barrel defining a barrel axisextending from a breach end to a muzzle end; b) A number of projectilesaxially stacked along the barrel axis; and, c) A number of charges, eachcharge being associated with a respective projectile, and being adaptedto urge the respective projectile along the barrel to thereby deploy theprojectile, the method including selectively activating the charges tothereby generate the selected projectile deployment pattern. 49.(canceled)